Internally cooled dilution hole bosses for gas turbine engine combustors

ABSTRACT

A cooling arrangement provides cooling around a dilution hole defined in a liner circumscribing a combustion chamber of a gas turbine engine. The cooling arrangement comprises a hollow boss projecting from an outer surface of the liner about the dilution hole. The hollow boss defines an internal cavity extending circumferentially around the dilution hole. The internal cavity has an inlet in fluid flow communication with an air plenum surrounding the liner and an outlet in fluid flow communication with the combustion chamber.

RELATED APPLICATIONS

The present application is a continuation of U.S. patent applicationSer. No. 14/843,197 filed on Sep. 2, 2015, the content of which isincorporated herein by reference.

TECHNICAL FIELD

The application relates generally to gas turbine engines and, moreparticularly, to cooling around combustor dilution holes.

BACKGROUND OF THE ART

Combustor dilution holes create strong jets of air that drives specificcharacteristics of the burning gasses within the combustion chamber.These jets generate large recirculation zones and wakes on the hotsurface of the surrounding combustor liner. This makes the region bothhotter and more difficult to cool. Residual cooling film from upstreamregions, if any, is easily blown away once it nears these features.Additional cooling air would help keep metal temperatures in designrange. On the other hand, too much cooling air exhausted around thesejets can interfere with the combustion process which is alsoundesirable. Due to limited space between holes and often awkwardgeometry, some regions cannot channel sufficient air. High metaltemperatures around these dilution holes cause significant oxidationand/or cracking; leading to poor quality jets which eventually lead toperformance changes within the combustor.

SUMMARY

Therefore, in accordance with one aspect, there is provided a combustorfor a gas turbine engine, the combustor comprising a liner defining acombustion chamber, the liner having an inner surface facing thecombustion chamber and an outer surface opposite the inner surface, aset of dilution holes extending through the liner, and a correspondingset of hollow bosses integral to the liner and extending aboutrespective ones of the dilution holes, each hollow boss defining aninternal cavity extending about the associated dilution hole, eachhollow boss having an inlet defined in the outer surface of the linerfor admitting cooling air into the internal cavity and an outletextending through the inner surface of the liner for discharging thecooling air from the internal cavity into the combustion chamber.

In accordance with another general aspect, there is provided a coolingarrangement for providing cooling around a dilution hole defined in aliner circumscribing a combustion chamber of a gas turbine engine, thecooling arrangement comprising: a hollow boss projecting from an outersurface of the liner about the dilution hole, the hollow boss definingan internal cavity extending circumferentially around the dilution hole,the internal cavity having an inlet in fluid flow communication with anair plenum surrounding the liner and an outlet in fluid flowcommunication with the combustion chamber.

In accordance with a still further general aspect, there is provided acombustor for a gas turbine engine, the combustor comprising a linerdefining a combustion chamber, the liner having an inner surface facingthe combustion chamber and an outer surface opposite the inner surface,a dilution hole extending through the liner, a boss integrally formed inthe liner about the dilution hole, the boss defining an internal cavityin the liner around the dilution hole, a set of inlet holes defined inthe outer surface of the liner for admitting cooling air into theinternal cavity, and a set of outlet holes defined in the inner surfaceof the liner for discharging the cooling air from the internal cavityinto the combustion chamber.

DESCRIPTION OF THE DRAWINGS

Reference is now made to the accompanying figures in which:

FIG. 1 is a schematic cross-section view of a gas turbine engine;

FIG. 2 is an isometric cross-section view of a portion of a combustorliner illustrating bosses integrally formed in the combustor liner aboutrespective dilution holes, each boss defining an internal cavity forreceiving cooling air from a plurality of inlet holes on a cold side ofthe combustor, outlet holes being provided on the hot side of thecombustor for discharging the cooling air from the internal cavity ofthe bosses;

FIG. 3 is a cold outer side view of the bosses shown in FIG. 2;

FIG. 4 is a hot inner side view illustrating a boss internal cavity andthe outlet holes thereof;

FIG. 5 is a cold outer side view of a boss which has been widened in onedirection to cool a larger surface area around the dilution hole;

FIG. 6 is a section view of the hollow boss shown in FIG. 5 illustratingfilm holes and trip-trips in the boss cavity;

FIG. 7 is an isometric cross-section view of a boss sectioned axially toshow trip-strips in the boss cavity on the underside of the combustorliner;

FIG. 8 is a cold outer side view of bosses which have been connected toeach other; and

FIG. 9 is a section view of the hollow bosses shown in FIG. 8illustrating internal cavities which have been connected to each other.Also shown is an internal cavity which does not completely surround adilution hole.

DETAILED DESCRIPTION

FIG. 1 illustrates a turbofan gas turbine engine 10 of a type preferablyprovided for use in subsonic flight, generally comprising in serial flowcommunication a fan 12 through which ambient air is propelled, amultistage compressor 14 for pressurizing the air, a combustor 16 inwhich the compressed air is mixed with fuel and ignited for generatingan annular stream of hot combustion gases, and a turbine section 18 forextracting energy from the combustion gases.

The combustor 16 is housed in a plenum 17 supplied with compressed airfrom compressor 14. The combustor 16 comprises a liner 20 defining acombustion chamber 21. The liner 20 has a hot inner surface 22 facingthe combustion chamber 21 and a back surface or cold outer surface 24facing the plenum 17. The combustor liner 20 typically includes one ormore rows of apertures, known as dilution holes 26, which allow aportion of the air from the plenum 17 to enter the combustion chamber 21and mix with burning gases. The dilution holes 26 are not to be confusedwith the cooling holes (not shown) extending through the liner forcooling the same. The dilution holes 26 are used to introduce dilutionair into the combustion zone of the combustor. The dilution air quenchesthe flames so as to control the gas temperature to which the turbinehardware downstream of the combustor will be exposed. The quenching alsoreduces the level of NOx emissions in the engine exhaust. The dilutionholes 26 are generally far smaller in number than the cooling holes, andeach dilution hole 26 has a cross-sectional area that is substantiallygreater than the cross-sectional area of one of the cooling holes. Thedilution holes 26 are typically arranged in a circumferentiallyextending row. As mentioned hereinbefore, the dilution holes 26 createstrong jets of air that drives specific characteristics of the burninggasses within the combustion chamber 21. The dilution air generateslarge recirculation zones and wakes on the inner surface 22 of the liner20. This makes the region around the dilution holes 26 more difficult tocool.

As shown in FIG. 2, a hollow boss 28 that incorporates internal passageswith cooling air may be integrally formed in the liner 20 about eachindividual dilution hole 26 to maximize heat removal about the dilutionholes 26.

More particularly, according to the embodiment shown in FIGS. 2 to 4,each boss 28 integrally projects from the outer surface 24 of the liner20 about a corresponding one of the dilution holes 26. In theillustrated embodiment, each boss 28 has a low profile donut shape.However, it is understood that the bosses 28 could adopt other suitableconfigurations. Each boss 28 defines an internal cavity 30 around theassociated dilution hole 26. According to the illustrated embodiment,the internal cavity 30 is provided in the form of an annulus with anoblong cross-section. It is understood that the internal cavity 30 maybe even more widened in any desired direction away from the dilutionhole 26 to provide cooling over a larger surface area. Notably, the bossand its internal cavity can be widened in a downstream directionrelative to the combustion gases flowing through the combustor. This canfor instance be appreciated from FIGS. 5 and 6. The internal cavity 30extends circumferentially continuously about the dilution hole 26. FromFIGS. 2 to 4, it can be appreciated that each internal cavity 30encircles the associated dilution hole 26.

Each internal cavity 30 has an inlet for allowing cooling air in theplenum 17 to flow therein. For instance, a circular array of uniformlydistributed inlet holes 32 may be defined atop of each boss 28. Thedistribution of the inlet holes 32 may however vary over the outersurface area of the boss as for instance shown in FIG. 5. Each internalcavity 30 also has an outlet for discharging the spent cooling air intothe combustion chamber 21. For instance, a set of outlet holes 34 mayextend from the internal cavity 30 through the inner surface 22 of theliner 20 to the combustion chamber 21 around each dilution holes 26.Each set of outlet holes 34 is in fluid flow communication with acorresponding one of the boss internal cavity 30 for discharging thecooling air circulated therethrough into the combustion chamber 21.

According to the illustrated embodiment, the inlet holes 32 are providedin the form of impingement holes oriented to direct impingement jetsagainst the back surface (i.e. the cold outer surface 24) of the liner20 within the boss internal cavities 30. Heat transfer augmentationfeatures 35 (FIGS. 6, 7 and 9), such as trip-strips or pin-fins, couldbe provided on the back surface of the liner 20 within each bossinternal cavity 30.

The outlet holes 34 may be provided in the form of film holes forforming a cooling film on the inner surface 22 of the combustor liner20. The film holes do not have to be straight—they can be curved to formlonger cooling passages, and their exits can be located furtherdownstream.

In operation, cooling air from the plenum 17 enters the inlet holes 32from the cold outer surface 24 of the liner 20. The air flowing throughthe inlet holes 32 impinges against the back side of the liner withinthe boss internal cavities 30. Then, the cooling air follows a curved orshaped passage (i.e. internal cavity 30) around each dilution hole rimin the liner 20 before exiting into the combustion chamber 21 via outletholes 34. The cooling air passing through the outlet holes 34 providesfor the formation of a cooling film on the inner surface 22 of the liner20. The curved or annular shape of the internal cavity 30 conforms tothe boss 28, enabling a more even temperature distribution. Thisprovides for increase cooling effectiveness around the combustordilution holes 26 and, thus, better durability of the combustor liner20. This is particularly true for single skin combustors.

As shown in FIGS. 8 and 9, one or more bosses 28 may be connected by abridge 36. This allows internal cavities 30 to be connected to eachother by a connector 37. This configuration is advantageous when thedilution holes 26 are closely spaced. Also shown in FIG. 9 is a wall 38.This illustrates that the internal cavity 30 does not have to completelyencircle the dilution hole.

It is understood that other technologies, such as rifled holes, wormholes or internal impingement, can be combined to make the cooling evenmore effective. Also, the internal cavities 30 could be made wider tocover a larger surface area around the dilution holes 26 (FIGS. 5 and6). The bosses 28 could be locally thickened to incorporate othercooling features, such as impingement, pin fin, trip strip and any othersuitable heat transfer augmentation features (FIGS. 6 and 7).

The above description is meant to be exemplary only, and one skilled inthe art will recognize that changes may be made to the embodimentsdescribed without departing from the scope of the invention disclosed.Any modifications which fall within the scope of the present inventionwill be apparent to those skilled in the art, in light of a review ofthis disclosure, and such modifications are intended to fall within theappended claims.

1. A combustor for a gas turbine engine, the combustor comprising: aliner defining a combustion chamber, the liner having an inner surfacefacing the combustion chamber and an outer surface opposite the innersurface, a set of dilution holes extending through the liner, and a setof hollow bosses formed integrally on the outer surface of the linerand, wherein the set of hollow bosses comprises a corresponding hollowboss extending about a corresponding dilution hole of the set ofdilution holes, such that each hollow boss corresponds to each dilutionhole of the set of dilution holes, each corresponding hollow bossdefining an internal cavity extending about each corresponding dilutionhole, each hollow boss having an inlet defined in the outer surface ofthe liner for admitting cooling air into the internal cavity and aplurality of film holes extending through the inner surface of the linerand fluidly connecting the internal cavity to the combustion chamber,the film holes being angled relative to the liner and distributed in acircle pattern about the corresponding dilution hole for forming acooling film on the inner surface of liner, and wherein heataugmentation features are provided on the outer surface of the linerwithin at least one of the hollow bosses of the set of hollow bosses. 2.The combustor defined in claim 1, wherein the internal cavity of eachhollow boss at least partly encircles each corresponding dilution holeand is sealed therefrom.
 3. The combustor defined in claim 1, whereinthe internal cavity of each hollow boss is provided in the form of anannulus which is widened in a direction away from each correspondingdilution hole.
 4. The combustor defined in claim 1, wherein the heattransfer augmentation features are interspersed between the film holes.5. The combustor defined in claim 1, wherein the inlet comprises a setof impingement holes distributed atop of the set of hollow bosses.
 6. Acombustor for a gas turbine engine, the combustor comprising: a linerdefining a combustion chamber, the liner having an inner surface facingthe combustion chamber and an outer surface opposite the inner surface,a dilution hole extending through the liner, a boss integrally formed inthe liner about the dilution hole, the boss defining an internal cavityin the liner around the dilution hole, the internal cavity extendingover a surface area of the liner around the dilution hole, a set ofinlet holes defined in the outer surface of the liner for admittingcooling air into the internal cavity, and a set of film holes defined inthe inner surface of the liner for discharging the cooling air from theinternal cavity into the combustion chamber, the set of film holes beingdistributed over the surface area of the liner covered by the internalcavity.
 7. The combustor defined in claim 6, wherein the internal cavityis provided in the form of an annulus widened in a direction away fromthe dilution hole.
 8. The combustor defined in claim 6, wherein heattransfer augmentation features are provided on an internal cavitysurface of the boss.
 9. The combustor defined in claim 12, wherein theheat transfer augmentation features are interspersed between the filmholes.
 10. A cooling arrangement for providing cooling around a dilutionhole defined in a liner circumscribing a combustion chamber of a gasturbine engine, the cooling arrangement comprising: a hollow bossprojecting from an outer surface of the liner about the dilution hole,the hollow boss defining an internal cavity extending circumferentiallyaround the dilution hole, the internal cavity being sealed from thedilution hole defined in the liner, the internal cavity having an inletin fluid flow communication with an air plenum surrounding the liner anda plurality of film holes distributed in circular pattern about thedilution hole and angled with respect to the liner to promote theformation of coolant film on an inner surface of the liner.
 11. Thecooling arrangement defined in claim 10, wherein the inlet comprises aset of impingement holes defined in the boss and oriented to directimpingement jets directly against the outer surface of the liner withinthe internal cavity.